EP1312807B1 - Rotor blade for centrifugal compressor - Google Patents

Rotor blade for centrifugal compressor Download PDF

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Publication number
EP1312807B1
EP1312807B1 EP02257848A EP02257848A EP1312807B1 EP 1312807 B1 EP1312807 B1 EP 1312807B1 EP 02257848 A EP02257848 A EP 02257848A EP 02257848 A EP02257848 A EP 02257848A EP 1312807 B1 EP1312807 B1 EP 1312807B1
Authority
EP
European Patent Office
Prior art keywords
rotor
axis
blade
lines
coordinates
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP02257848A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1312807A3 (en
EP1312807A2 (en
Inventor
Eugenio Rossi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nuovo Pignone Holding SpA
Nuovo Pignone SpA
Original Assignee
Nuovo Pignone Holding SpA
Nuovo Pignone SpA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nuovo Pignone Holding SpA, Nuovo Pignone SpA filed Critical Nuovo Pignone Holding SpA
Publication of EP1312807A2 publication Critical patent/EP1312807A2/en
Publication of EP1312807A3 publication Critical patent/EP1312807A3/en
Application granted granted Critical
Publication of EP1312807B1 publication Critical patent/EP1312807B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes

Definitions

  • the present invention relates to a rotor blade for a centrifugal compressor with a medium-high flow coefficient such as disclosed in FR 933.259.
  • the invention relates to a cylindrical blade for a centrifugal rotor of a multi-stage compressor with a medium-high flow coefficient.
  • This dimensionless coefficient can be used to define the operating characteristic of the compressor, and can be used to classify the different types of compressor at the design stage.
  • Compressors are therefore made to handle different flow rates, in other words to operate with different values of the flow coefficient, according to the applications for which they are intended.
  • compressors with a medium flow coefficient are defined as those in which ⁇ has values in the vicinity of 0.04, and compressors with a medium-high flow coefficient are defined as those for which ⁇ is approximately 0.06.
  • the geometric configuration of the rotor blading significantly affects the aerodynamic efficiency, due to the fact that the geometric characteristics of the blade determine the distribution of the relative velocities of the fluid along the rotor, thus affecting the distribution of the boundary layers along the walls and, in the final analysis, the friction losses.
  • the aerodynamic efficiency is particularly critical for rotors made with stages having two-dimensional blades, in other words purely radial rotors in which the blades are flat or cylindrical with generatrices parallel to the axis of rotation.
  • the blades used in this type of rotor have a relatively simple geometry in which the median line of the section consists of an arc of a circumference and the thickness is constant along the blade, except in the region of the leading edge, which is formed by a semicircular fillet or, in particular cases, by a tapering of the thickness.
  • the present invention therefore seeks to provide a blade which, by means of a suitable configuration, enables a high aerodynamic efficiency to be achieved.
  • the present invention also seeks to provide a blade which can be manufactured economically on a large scale by automated processes.
  • a cylindrical blade for a rotor of the purely radial type of a centrifugal compressor with a medium-high flow coefficient the blade being positioned between a disc and a counter-disc forming the rotor, and comprising a first surface of the pressure side and a second surface of the suction side having equal curvature, both having generatrices parallel to the axis (Z) of rotation of the rotor, the lines of curvature of the said surfaces being defined, in the direction of the axis (Z), by a first section of the blade in contact with the counter-disc, and by a second section of the blade in contact with the disc, characterized in that, in a right-hand Cartesian reference system (Y, X, Z) having an axis of ordinates (X) and an axis of abscissae (Y), with the plane (YX) coinciding with the said second contact section, and with the axis (Z) coinciding with the axis
  • a rotor 20 of the purely radial type with an outer radius R belonging to a centrifugal compressor with a medium-high flow coefficient comprises a plurality of cylindrical blades 1 positioned between a disc 21 and a counter-disc 22.
  • the blades 1 are made, by an established technique, in one piece with the said disc 21 and/or counter-disc 22, or are applied to the disc 21.
  • Each blade 1 comprises a first surface 3 of the pressure side facing forwards with respect to the direction of rotation of the rotor, indicated by the arrow F in Figure 1, and a second surface 5 of the suction side, opposite the first surface.
  • the surfaces 3 and 5 are cylindrical, and are made essentially with equal curvature and with generatrices parallel to the axis Z of rotation of the rotor 20.
  • the two surfaces 3 and 5 are joined together at one end by a leading edge 4, located at the suction inlet of the rotor, formed by a tapering of the thickness of the blade 1.
  • the aforesaid surfaces 3 and 5 terminate in a transverse edge 2, flush with the outer circumference of the disc 21 and the counter-disc 22.
  • the blade 1 has, at its junction with the disc 21, a first section 9 which is flat and lies on a plane Y,X of a right-handed Cartesian system having an axis of abscissae Y, an axis of ordinates X and an axis Z coinciding with the axis of rotation of the rotor and orientated towards the inside of the machine.
  • the origin O of this reference system lies at the intersection of the plane Y, X, on which the joining section 9 lies, with the axis of rotation of the rotor.
  • the blade 1 is joined to the counter-disc 22 in a second section 7 which is curved, according to the known art, in the proximity of the leading edge 4 in such a way as to follow the curvature of the counter-disc 22 at the inlet of the rotor.
  • the blade 1 is of the cylindrical type, the projections on the plane Y, X of the sections 7 and 9 are essentially coincident.
  • the profile of the blade 1, and consequently its curvature, are therefore identified by the intersection of the said surfaces 3 and 5 with the plane Y, X.
  • the intersection of the surfaces 3 and 5 with the section 7 forms two curved lines, namely a first edge line 6 on the pressure side and a second edge line 8 on the suction side, determined by a discrete set of points 10 belonging to them, whose coordinates x, y, z with respect to the three axes Y, X, Z are conveniently expressed as a function of the outer radius R of the rotor 20.
  • the intersection of the surfaces 3 and 5 with the section 9 forms two curved lines, namely a third edge line 6' on the pressure side and a fourth edge line 8' on the suction side.
  • the edge lines 6' and 8' are defined by the same x and y coordinates as those of the corresponding lines 6 and 8, while they have a z coordinate of zero for all the points lying on them.
  • the surfaces 3 and 5, and essentially the blade 1, can be conveniently formed by means of automatic machines, for example those of the numerically controlled type, or the like.
  • the rotor 20 and correspondingly the blades 1 can also be made in various sizes.
  • the characteristics of a rotor are, within certain limits, essentially dependent on the curvature of the blades, and are therefore, as a first approximation, equal for similar rotors.
  • the lines 6 and 8 of the blade 1 according to the invention expressed in each case as a function of the outer radius R of the rotor, in the form of the ratios y/R, x/R and z/R between the values of the coordinates of each point 10 and the value of the said radius R, are defined by the following values, for the line 6:
  • a rotor 20 for a compressor with a medium-high flow coefficient was made with an outer radius of 200 mm and with 19 cylindrical blades 1 whose surfaces 3 on the pressure sides and surfaces 5 on the suction sides have equal curvature.
  • These surfaces 3 and 5 are defined, in a right-hand system of Cartesian axes Y, X, Z having an axis of abscissae Y, an axis of ordinates X and an axis Z coinciding with the axis of rotation of the rotor and orientated towards the inside of the machine, by the following coordinates x, y, z of a discrete set of points 10 belonging to the edge lines 6 and 8 generated respectively by the surfaces 3 and 5 at the intersection with the section 7 of the blade 1 in contact with the counter-disc 22 of the rotor.
  • the line 6 is defined by points 10 having the following coordinates:
  • the line 8 is defined by points 10 having the following coordinates:

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Medicines That Contain Protein Lipid Enzymes And Other Medicines (AREA)
  • Materials For Photolithography (AREA)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
EP02257848A 2001-11-15 2002-11-14 Rotor blade for centrifugal compressor Expired - Lifetime EP1312807B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT2001MI002414A ITMI20012414A1 (it) 2001-11-15 2001-11-15 Pala per girante di compressore centrifugo a medio-alto coefficiente di flusso
ITMI20012414 2001-11-15

Publications (3)

Publication Number Publication Date
EP1312807A2 EP1312807A2 (en) 2003-05-21
EP1312807A3 EP1312807A3 (en) 2003-12-03
EP1312807B1 true EP1312807B1 (en) 2007-03-21

Family

ID=11448610

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02257848A Expired - Lifetime EP1312807B1 (en) 2001-11-15 2002-11-14 Rotor blade for centrifugal compressor

Country Status (7)

Country Link
US (1) US6729845B2 (ja)
EP (1) EP1312807B1 (ja)
JP (1) JP2003184789A (ja)
AU (1) AU2002301913B2 (ja)
DE (1) DE60218959T2 (ja)
IT (1) ITMI20012414A1 (ja)
NO (1) NO330378B1 (ja)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8313300B2 (en) * 2007-06-14 2012-11-20 Christianson Systems, Inc. Rotor for centrifugal compressor
TR201901181T4 (tr) * 2013-03-28 2019-02-21 Weir Minerals Australia Ltd Sulu çamur pompası çarkı.
CN105121864B (zh) * 2013-06-20 2017-06-09 三菱重工业株式会社 离心式压缩机
JP5705945B1 (ja) * 2013-10-28 2015-04-22 ミネベア株式会社 遠心式ファン
UA119693C2 (uk) * 2017-07-28 2019-07-25 Андрій Іванович Панфілов Робоче колесо відцентрового двостороннього вентилятора
US20200378303A1 (en) * 2019-06-03 2020-12-03 Pratt & Whitney Canada Corp. Diffuser pipe exit flare
US11754088B2 (en) 2021-12-03 2023-09-12 Hamilton Sundstrand Corporation Fan impeller with thin blades

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR933259A (fr) * 1945-09-15 1948-04-15 Brown Bovery Sa Procédé de fabrication de roues centrifuges dans lesquelles les ailettes forment une seule pièce avec le disque de recouvrement, en particulier pour compresseurs et pompes, ainsi que roue centrifuge fabriquée suivant ce procédé
CH519109A (fr) * 1965-03-03 1972-02-15 Masukichi Kondo Aube de rotor
JPS61109608A (ja) * 1984-11-01 1986-05-28 Mitsubishi Heavy Ind Ltd 羽根車の加工方法
US4666373A (en) * 1986-03-20 1987-05-19 Eiichi Sugiura Impeller for rotary fluid machine
EP1013938B1 (de) * 1998-12-18 2001-08-01 Lothar Reckert Gebläserad mit geringer spezifischer Drehzahl

Also Published As

Publication number Publication date
AU2002301913B2 (en) 2009-01-15
ITMI20012414A1 (it) 2003-05-15
JP2003184789A (ja) 2003-07-03
NO330378B1 (no) 2011-04-04
NO20025446D0 (no) 2002-11-14
EP1312807A3 (en) 2003-12-03
DE60218959D1 (de) 2007-05-03
US6729845B2 (en) 2004-05-04
NO20025446L (no) 2003-05-16
US20030091439A1 (en) 2003-05-15
EP1312807A2 (en) 2003-05-21
DE60218959T2 (de) 2007-11-29

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